CN1982657A - Methods and apparatus for assembling steam turbines - Google Patents

Methods and apparatus for assembling steam turbines Download PDF

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Publication number
CN1982657A
CN1982657A CNA2006101719794A CN200610171979A CN1982657A CN 1982657 A CN1982657 A CN 1982657A CN A2006101719794 A CNA2006101719794 A CN A2006101719794A CN 200610171979 A CN200610171979 A CN 200610171979A CN 1982657 A CN1982657 A CN 1982657A
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CN
China
Prior art keywords
turbine
turbine diaphragm
aerofoil
diaphragm
hole
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CNA2006101719794A
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Chinese (zh)
Other versions
CN1982657B (en
Inventor
S·S·伯德吉克
B·I·弗罗洛夫
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
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General Electric Co
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Filing date
Publication date
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Publication of CN1982657A publication Critical patent/CN1982657A/en
Application granted granted Critical
Publication of CN1982657B publication Critical patent/CN1982657B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49947—Assembling or joining by applying separate fastener
    • Y10T29/49966—Assembling or joining by applying separate fastener with supplemental joining
    • Y10T29/49968—Metal fusion joining

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Method and apparatus for assembling steam turbines are provided. The method of assembling a steam turbine includes providing an annular outer member, providing an annular inner member, coupling a plurality of airfoils to the inner member with a plurality of generally radial fastener assemblies such that the plurality of airfoils extend substantially radially outward from the inner member, and coupling each of the plurality of airfoils to the outer member.

Description

The method and apparatus of assembling steam turbines
Technical field
Present invention relates in general to steam turbine, especially relate to the method and apparatus of assembling steam turbines.
Background technique
At least some known steam turbines comprise a turbine structure, and this structure has the multistage turbine diversion disk.At least in these known turbo machines, last what turbine diaphragm is called as fillet weld structure (fillet fabrication), this structure is by ring, a plurality of circumferentially aerofoil spaced and that extend between two annular construction members, dividing plate in the outer shroud, one, and/or nozzle constitutes.For the ease of improving the structural integrity of described turbine diaphragm, aerofoil is soldered on interior ring and the outer shroud.More specifically, for the ease of reaching predetermined weld strength, known fillet weld structure comprises a big fillet weld that is positioned on the interface that is limited by aerofoil and ring.
In the process of making these known fillet weld structures, the water passage surface of ring and outer shroud in before the aerofoil that each is independent is welded on the precalculated position, will marking earlier.But because known aerofoil is generally very heavy and be difficult to manipulation, welding process is not only time-consuming but also require great effort.In other known manufacture method, use a kind of fixing device of complexity during welding so that aim at and the maintenance aerofoil.But known fixing device is very expensive.In addition, every kind of manufacture method, the welding deformation that in making the process of turbine diaphragm, all can have local heating and contraction owing to scolder to cause.So, usually need the operation of a large amount of manual-alignment and/or the turbine diaphragm of having assembled carried out machining to guarantee the tolerance of being scheduled to and meet the demands by circumferential adjacent throat's boundary that aerofoil limited (throat limitation).In addition, the aerofoil of distortion or ring generally can not obtain the tolerance of being scheduled to fully, and like this, the performance of that grade may be given a discount.
Summary of the invention
A kind of method of assembling steam turbines is provided on the one hand.This method comprises the outer member that an annular is provided, the inner member of an annular is connected to a plurality of aerofoils on the inner member, with a plurality of securing meanss like this, a plurality of aerofoils extend radially outward basically from inner member, and each aerofoil is linked on the outer member.
A kind of turbine diaphragm of steam turbine is provided on the other hand.This turbine diaphragm comprises radial outside and the radially inner side member that is configured to basically in steam turbine inside along extending circumferentially, and at least one aerofoil that radially extends basically between the outside and inner member.With a securing means this at least one aerofoil is linked on one in radial outside member and the radially inner side member.
On the one hand, provide a kind of steam turbine again.This steam turbine comprises at least one turbine diaphragm, and this turbine diaphragm comprises radial outside and the radially inner side member that is configured to basically in steam turbine inside along extending circumferentially, and a plurality of aerofoil that extends between the outside and inner member.A plurality of aerofoils are arranged and are connected on one in the outside and the inner member by a securing means along circumferential each interval.
Description of drawings
Fig. 1 is a kind of convection type of exemplary known or the schematic representation of double-current method steam turbine;
Fig. 2 is the enlarged diagram of a kind of exemplary turbine diaphragm that can use with steam turbine shown in Figure 1;
Fig. 3 is the enlarged diagram of a part of turbine diaphragm among Fig. 2; With
Fig. 4 be among Fig. 3 turbine diaphragm at zone 4 enlarged diagram.
Embodiment
Fig. 1 is a kind of schematic representation of convection type steam turbine 10 of exemplary known.Turbo machine 10 comprises first and second low pressure (LP) joint 12 and 14.Well known in the art, each turbine section 12 and 14 all comprises multistage turbine diversion disk (Fig. 1 is not shown).Rotor shaft 16 extends through turbine section 12 and 14.Each LP joint 12 and 14 all has a nozzle 18 and 20.Independent shell or housing 22 are divided into upper shell 24 and lower shell body 26 respectively in the axial direction along a horizontal plane, and across these two low pressure joints 12 and 14.The intermediate section 18 of housing 22 is provided with a low pressure steam inlet 30.In shell or housing 22, LP joint 12 and 14 carries out single shaft by sliding bearing 32 and 34 respectively and holds across supporting.Shunt 40 extends between first and second turbine sections 12 and 14.
Only illustrated a kind of low pressure twin turbine though should be appreciated that Fig. 1, but as those skilled in the art, the present invention is not limited to only be used on the low-pressure turbine, the twin turbine that it also can be used for other includes but not limited to middle pressure (IP) turbo machine or high pressure (HP) turbo machine.In addition, the present invention also is not limited to and is used on the twin turbine, for example, is more suitable for being used for single-flow turbine.
In running, low pressure steam inlet 30 is by one. and cross over the pipe (not shown) and receive, for example the low pressure of HP turbo machine or IP turbo machine/middle temperature steam 50 from steam source.Described steam 50 is conducted through inlet 30, and wherein, shunt 40 is divided into two relative runners 52 and 54 with vapor stream.More specifically, steam 50 flows through LP joint 12 and 14, wherein, extracts merit and come drives rotor shaft 16 to rotate from steam.Steam also for example flows out LP joint 12 and 14, is drawn towards a middle-pressure turbine (not shown).
Fig. 2 is the enlarged diagram of a kind of exemplary turbine diaphragm 100 that can use with steam turbine 10 (as shown in Figure 1).In one embodiment, turbine diaphragm 100 is afterbody turbine diaphragm 100 of turbo machine 10.Turbine diaphragm 100 comprises the outer shroud 104 of an inner annular plate or 102, one annulars of interior ring, and a plurality of nozzles that extend between them or aerofoil 106.Outer shroud 104 is positioned at the radial outside of ring 102, and substantially concentric with interior ring.Nozzle 106 circumferentially is spaced between ring 102 and 104 and radially extends basically between inner and outer rings 102 and 104 respectively.
In the inner radial surface 112 of ring 102 radially-outer surface 110 and outer shroud 104 define radial inner edge circle of the runner that limits by turbine diaphragm 100 and external boundary radially.
Fig. 3 is the enlarged diagram of a part of turbine diaphragm 100.Fig. 4 is the enlarged diagram of turbine diaphragm 100 in zone 4.In this embodiment, ring 102 is made of a roll extrusion ring or forging ring in the turbine diaphragm.Alternately, ring 102 can constitute by the means that any feasible ring 102 has function described here in the turbine diaphragm.Ring 102 comprises a plurality of mating holes 111 and a plurality of attachment hole 112.In this embodiment, hole 111 is pin-and-holes, and hole 112 is screws.Hole 111 and 112 all encircles 102 basically in radially passing between the inner radial surface 114 of water passage surface 110 and interior ring 102.
Hole 111 and 112 circumferentially is spaced on interior ring 102.More specifically, in this embodiment, hole 111 is positioned at the downstream and the span D in hole 112.Alternately, hole 111 can be formed on any position of being convenient to assemble turbine diaphragm 100 described herein with respect to hole 112.In addition, in this embodiment, the diameter d in hole 111 aDiameter d less than each hole 112 oAlternately, diameter d aBe approximately equal to or greater than the diameter d of attachment hole oMore specifically, in this embodiment, each bore dia d aBe approximately equal to the diameter d that each inserts alignment pin 130 wherein p
In this embodiment, mating holes 111 is drilled to by the course of working of precision.Alternately, hole 111 can form by any process that makes hole 111 have function described here.Particularly, the position in hole 111 is convenient to determine along the circumferential spacing between the circumferentially adjacent aerofoil 106 of inner flow passage.In addition, the position in hole 111 also is convenient to aim at aerofoil 106 in the axial direction with respect to interior ring 102, more specifically with respect to water passage surface 110.For example, in an alternate embodiment, hole 111 is positioned at the place ahead in hole 112.
Hole 112 circumferentially is spaced on interior ring 102, each hole all have one from internal surface 114 towards water passage surface 110 grooves that extend internally or taper hole part 140.Between taper hole part 140 and water passage surface 110, the diameter d in hole 112 oDiameter d less than taper hole part 140 CsIn this embodiment, the diameter d of taper hole part CsDiameter d greater than the connecting bolt 150 that it held Bh, and bore dia d oDiameter d greater than corresponding connecting bolt bar 152 Bb
In this embodiment, attachment hole 112 is drilled to by the course of working of precision.Alternately, hole 112 can form by any process that makes hole 112 have function described here.Particularly, the throat opening area between circumferentially adjacent aerofoil 106 is convenient to determine in the position in hole 112.In this embodiment, hole 112 can be more bigger so that allow tiny aligning correction when independent throat region is set.
In the process of making turbine diaphragm 100, radially form hole 111 and 112 basically for 102 li at interior ring earlier.Then first aerofoil 106 is positioned on its pairing interior surface, circulation road 110, in corresponding mating holes 111, is inserting alignment pin 130 slidably then.More specifically, alignment pin 130 can radially insert basically from internal surface 141, and ring 102 in passing inserts the aerofoil 106 that is positioned on the water passage surface 110 then.Each pin 130 is all joined tightly by friction with corresponding hole 111.Pin 130 both had been convenient to aerofoil 106 each other along circumferential location, also was of value to aerofoil with respect to location vertically, surface, interior circulation road 110.Alternately, a plurality of pins 130 are used to be convenient to the aligning of aerofoil 106 with respect to other aerofoil.
Aerofoil 106 then forms attachment hole 112 with respect to turbine diaphragm 100 location in interior ring 102 and aerofoil 106 then.In this embodiment, tap out on the part 140 in the hole 112 that limits by aerofoil 106.Each connecting bolt 150 inserts in each hole 112 so that each aerofoil 106 is fixed on interior the ring on 102.More specifically, if bolt 150 is threaded in each aerofoil 106, the direction that so still will rotate aerofoil 106 a little is to adjust the throat region of individual nozzle.In an alternate embodiment, a plurality of bolts 150 are used to be convenient to aerofoil 106 is fixed on interior ring 102.
After defining each aerofoil throat region, each aerofoil 106 is positioned and is welded on the outer shroud 104 so that guarantee that the direction of aerofoil 106 is consistent with the direction that other is connected the aerofoil 106 on the turbine diaphragm 100.Set after the throat region, connecting bolt 150 is fastened in the hole 112, and the head 170 of each bolt 150 just is contained in the taper hole part 140 in each hole like this.Just can not produce any convection cell flows through unnecessary ring, edge or the projection that turbine diaphragm 100 has negative effect to bolt 150 like this.
Aerofoil 106 circumferentially be spaced around interior ring 102 and outer shroud 104 be positioned be welded on each aerofoil 106 in the turbine diaphragm 100 after, aerofoil 106 also just has been welded on the outer shroud 104 regularly.In one embodiment, form a plurality of additional mating holes (not shown) so that aerofoil 106 fixing in final direction.More specifically, aerofoil 106 is not in the circumferential continuous welding of turbine diaphragm 100, but so that welding and reduce that the mode of welding deformation welds.
So, make turbine diaphragm with the method that a kind of manufacture method than known turbine diaphragm is more low-cost, more not time-consuming.Especially,, in manufacture process, just reduced the welding on the turbine diaphragm 100, like this,, just shortened and made turbine diaphragm 100 required cycle time than known turbine diaphragm because turbine diaphragm 100 has the interior ring 102 of a strap bolt.In addition, because interior ring attachment hole 112 is excessive a little, hole 112 is convenient to a kind of than the more accurate qualification throat region of the more cost-effective mode of known turbine diaphragm.So, be convenient to improve the performance and the efficient of turbo machine.In addition, because turbine diaphragm 100 desired welding capacity little than known turbine diaphragm just reduced the welding deformation in the turbine diaphragm 100, be convenient to improve the performance of turbo machine like this.
Described the embodiment of steam turbine and turbine diaphragm above in detail.Though turbine diaphragm is described as relevantly with above-mentioned steam turbine herein, is understood that the present invention also can be used for other steam turbine structure.More specifically, turbine diaphragm is not limited to the above-mentioned specific embodiment of this paper, and the feature of each turbine diaphragm more can be separated independent the use with other turbo machine as herein described or turbine diaphragm.
Though the present invention is illustrated by multiple embodiment, it will be appreciated by those skilled in the art that can also make multiple change in the scope of spirit of the present invention and claim realizes the present invention.

Claims (10)

1. turbine diaphragm (100) that is used for steam turbine, described turbine diaphragm comprises:
A radial outside member (104) that is configured in described steam turbine (10) basically along extending circumferentially;
A radially inner side member (102) that is configured in described steam turbine basically along extending circumferentially; With
The aerofoil (106) that at least one radially extends between the described outside and inner member is basically linked described at least one aerofoil in described radial outside and the radially inner side member one with a securing means.
2. turbine diaphragm as claimed in claim 1 (100), wherein, described at least one aerofoil (106) is welded in described radial outside and the radially inner side member (102,104) one.
3. turbine diaphragm as claimed in claim 1 (100), wherein, described securing means comprises at least one alignment pin (130) and at least one bolt (150).
4. turbine diaphragm as claimed in claim 1 (100), wherein, one in described radially inner side member (102) and the radial outside member (104) comprises a plurality of holes of running through wherein (111), and described a plurality of holes are convenient to aim at described at least one aerofoil (106) with respect to described turbine diaphragm.
5. turbine diaphragm as claimed in claim 1 (100), wherein, described securing means helps reducing the welding deformation in the turbine diaphragm.
6. turbine diaphragm as claimed in claim 1 (100), wherein, described securing means helps reducing the built-up time of described turbine diaphragm.
7. turbine diaphragm as claimed in claim 1 (100), wherein, described securing means helps improving the performance of turbo machine.
8. steam turbine (10) that comprises at least one turbine diaphragm (100), described turbine diaphragm comprises a radial outside member (104), a radially inner side member (102), and a plurality of aerofoils that between them, extend (106), described radial outside and inner member are configured in described turbo machine along extending circumferentially, and described a plurality of aerofoils are circumferentially linked in the described outside and the inner member one each other at interval and by a kind of securing means.
9. steam turbine as claimed in claim 8 (10), wherein, described a plurality of aerofoils (106) are soldered in described inner member (102) and the described outer member (104) one.
10. steam turbine as claimed in claim 8 (10), wherein, described inner member (102) comprises a plurality of circumferential spaced holes of running through wherein, edge (111), and described hole is convenient to aim in described a plurality of aerofoils (106) each with respect to described turbine diaphragm (100).
CN2006101719794A 2005-11-17 2006-11-17 Methods and apparatus for assembling steam turbines Expired - Fee Related CN1982657B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/281,641 US7654794B2 (en) 2005-11-17 2005-11-17 Methods and apparatus for assembling steam turbines
US11/281641 2005-11-17

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CN1982657A true CN1982657A (en) 2007-06-20
CN1982657B CN1982657B (en) 2011-09-07

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US (1) US7654794B2 (en)
JP (1) JP4912840B2 (en)
CN (1) CN1982657B (en)
CH (1) CH700013B1 (en)
DE (1) DE102006054684B4 (en)

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CN104364474A (en) * 2012-04-06 2015-02-18 诺沃皮尼奥内股份有限公司 Stator blade diaphragm ring, turbo-machine and method

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Also Published As

Publication number Publication date
CN1982657B (en) 2011-09-07
US7654794B2 (en) 2010-02-02
US20070110575A1 (en) 2007-05-17
DE102006054684B4 (en) 2021-05-20
JP4912840B2 (en) 2012-04-11
DE102006054684A1 (en) 2007-05-24
CH700013B1 (en) 2010-06-15
JP2007138936A (en) 2007-06-07

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